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    BAFFLE WITH IMPINGEMENT HOLES
    101.
    发明申请
    BAFFLE WITH IMPINGEMENT HOLES 有权

    公开(公告)号：US20210115801A1

    公开(公告)日：2021-04-22

    申请号：US16657135

    申请日：2019-10-18

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Adam P. Generale ,  Lucas Dvorozniak ,  San Quach

    IPC: F01D5/18 ,  F01D25/12

    Abstract: An airfoil includes an vane airfoil, which has a ceramic matrix composite airfoil section including an outer wall that defines an internal cavity. The vane airfoil has an associated temperature profile which defines at least one high temperature area and at least one low temperature area. The vane airfoil includes a first zone which is defined in a first radial extent and corresponds to the high temperature area of the temperature profile and a second zone defined in a second radial extent and corresponds to the low temperature area of the temperature profile. An insert is situated in the internal cavity. The insert includes a first zone defined in a first radial extent that is aligned with the first zone of the vane airfoil. The first zone includes a first plurality of cooling holes which are configured to provide a first cooling density. A second zone is defined in a second radial extent that is aligned with the second zone of the vane airfoil. The second zone includes a second plurality of cooling holes that provide a second cooling density that is lower than the first cooling density such that the high temperature area and the low temperature area are balanced to lower a thermal gradient across the first and second zones of the vane airfoil. An vane airfoil and a method of assembling a ceramic matrix composite vane airfoil are also disclosed.

    BAFFLE WITH TAIL
    102.
    发明申请
    BAFFLE WITH TAIL 有权

    公开(公告)号：US20210108519A1

    公开(公告)日：2021-04-15

    申请号：US16600875

    申请日：2019-10-14

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Adam P. Generale ,  Lucas Dvorozniak ,  San Quach ,  Bryan P. Dube

    IPC: F01D5/18

    Abstract: An airfoil vane includes an airfoil section including an outer wall that defines an internal cavity; and a baffle situated in the internal cavity, the baffle including a baffle wall that defines a central cavity having a leading end and a trailing end corresponding to a leading end and a trailing end of the airfoil section, and a tail extending from the baffle wall, the tail including at least one feature configured to disturb an airflow surrounding the tail. A baffle for the airfoil vane assembly and a method of assembling a ceramic matrix composite airfoil vane are also disclosed.

    Airfoil cooling circuits
    104.
    发明授权
    Airfoil cooling circuits 有权

    公开(公告)号：US10808551B2

    公开(公告)日：2020-10-20

    申请号：US16397180

    申请日：2019-04-29

    Applicant: United Technologies Corporation

    Inventor： Eric A. Hudson ,  Tracy A. Propheter-Hinckley ,  San Quach ,  Matthew A. Devore

    IPC: B22C9/10 ,  B22C9/24 ,  F01D5/18

    Abstract: An airfoil includes leading and trailing edges; first and second sides extending from the leading edge to the trailing edge, each side having an exterior surface; a core passage located between the first and second sides and the leading and trailing edges; and a wall structure located between the core passage and the exterior surface of the first side. The wall structure includes a plurality of cooling fluid inlets communicating with the core passage for receiving cooling fluid from the core passage, a plurality of cooling fluid outlets on the exterior surface of the first side for expelling cooling fluid and forming a cooling film along the exterior surface of the first side, and a plurality of cooling passages communicating with the plurality of cooling fluid inlets and the plurality of cooling fluid outlets. At least a portion of one cooling passage extends between adjacent cooling fluid outlets.

    Gas turbine engine turbine blade leading edge tip trench cooling
    107.
    发明授权
    Gas turbine engine turbine blade leading edge tip trench cooling 审中-公开

    公开(公告)号：US10655473B2

    公开(公告)日：2020-05-19

    申请号：US13713371

    申请日：2012-12-13

    Applicant: United Technologies Corporation

    Inventor： San Quach ,  Lane Thornton

    IPC: F01D5/18

    Abstract: An airfoil for a gas turbine engine includes pressure and suction walls spaced apart from one another and joined at leading and trailing edges to provide an airfoil having an exterior surface that extends in a radial direction to a tip. A tip trench is provided in the tip and wrapping at least a portion of the airfoil from the pressure side wall around the leading edge to the suction side wall. The tip trench is provided by a recess.

    Internal cooling cavity with trip strips
    108.
    发明授权
    Internal cooling cavity with trip strips 有权

    公开(公告)号：US10605094B2

    公开(公告)日：2020-03-31

    申请号：US14602035

    申请日：2015-01-21

    Applicant: United Technologies Corporation

    Inventor： San Quach ,  Atul Kohli ,  Matthew A. Devore ,  Steven Bruce Gautschi

    IPC: F01D5/18

    Abstract: An airfoil is provided. The airfoil may comprise a cross over, an impingement chamber in fluid communication with the cross over, and a first trip strip disposed on a first surface of the impingement chamber. A cooling system is also provided. The cooling system may comprise an impingement chamber, a first trip strip on a first surface of the impingement chamber, and a second trip strip on a second surface of the impingement chamber. An internally cooled engine part is further provided. The internally cooled part may comprise a cross over and an impingement chamber in fluid communication with the cross over. The cross over may be configured to direct air towards a first surface of the impingement chamber. A first trip strip may be disposed on the first surface of the impingement chamber.

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